Stabilization and control of rotating wing aircraft



Dec. 28,1943. s, PULU'N' 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet 1 INVEIVIWA Wfizzfz W rm Dec. 28, 1943. c pu 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet 2 Dec. 28, 1943. G] PULUN 2,337,570

STABILIZATION AND CONTROL OF RO'I'ATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet a J d? 44% if? E 612' 42a 42/ WC 3 k 4 5&6 ;l\/ T w /Z%\ 5/5 j v 601 L E 6/4 I 52/ I $5 //VVENTOR Dec. 28, 1943. I c. G. PULLIN 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet 4 nrrogusf W? Dec. Q G L N STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet 5 Dec. 28, 1943. c PULLlN I 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 SheetsSheet 6 AFT Dec. 28, 1943. c. G. PULLIN STABILIZATION AND CONTROL OF ROTATING WING AIRCR Filed April 24, 1940 15 Sheets-Sheet 8 INVENTOI? 7 22 f firrmwsrs Dec. 28, 1943. c. G. PULLIN 2,337,570

' STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 l5 Sheets-Sheet 9 427 J L v p 328- l/VYENTIA ATTOK/VEFS 1943. c. G. PULLlN 12,337,570

7 STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 194 15 Sheets-Sheet l0 @\OO@ O INVEN 70K ATTORNE Dec. 28, 1943. c G. PULUN 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed Apr il 24, 1940 15 Sheets-Sheet 11 IN VE/V T04 A 7'70AWEVS c. G. PULLIN 2,337,570

' STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet 12 1% gm k gig l/WENTOK fi ie f 2' ATE/wars Dec. 28, 1943. c, G 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24. 1940 15 Sheets-Sheet. l3

. "WE/970R A 770 NEVS W MW Dec. 28, 1943. 'c. a. PULLIN STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet l4 /NvE'NTOR A ORNE Y5 Dec. 28, 1943. c. s. PULLIN 2,337,570

STABILIZATION AND CONTROL OF ROTATING WING AIRCRAFT Filed April 24, 1940 15 Sheets-Sheet l5 m VENTOR Patented Dec. 1943 I areas-1o 1 STABILIZATION AND comet or ROTATING WING AIRCRAFT 'Cyril George 'Pullin, Genista, Newton Mearns, Scotland, assignor to Autogiro' Company of America,' Wiliow Grove, 2a., a corporation of Delaware Application- April 24, 1940, Serial No. 831,318 In Great Britain March 2, 1939 (Cl. 2441'l) 25 Claims.

The present invention relates to stabilization and control of rotating wing aircraft, and par-' ticularly to means for effecting the stability and control of rotating wing aircraft of the type having one or more pairs of normally power driven sustaining rotors disposed on opposite sides of the fuselage or body of the aircraft.

In aircraft having a pair of sustaining rotors driven at equal speeds from a common shaft through a gearbox and disposed on opposite sides of the fuselage it is possible under certain conditions for the lift of one of the rotors to exceed the lift of the other by an amount giving rise to dangerous overturning moments of the aircraft. These overturning moments may cause the aircraft to bank excessively to a position in which lateral control can no longer be maintained. An object ofthis invention is to provide means for preventing the setting up of such dangerous conditions so that control of the aircraft may be maintained.

According to the present invention substantial equality of the torque applied to each of a pair of rotors is maintained, at least under normal flight conditions while the rotors are being driven, by a balance gear, for instance of the differential type. This balance gear will be effective to maintain equality of torque in the pair of rotors except insofar as this balance of torque is affected by the mechanical imperfection of the balance gear and by the inertia of the rotors and transmission system. Moreover in the event of a failure of the transmission to one of the rotors the balance gear will relieve the other rotor of the drive and will spin idly.

It is most desirable that means should be provided permitting the rotors to continue revolving in the event of an engine or transmission failure so that suficient lift is maintained to allow the aircraft to be landed safely. This may be accomplished by providing means for disconnecting the engine from both the rotor transmissions for instance by manually or automatically disconnecting a clutch on the engine shaft or by including in this shaft a freewheel clutch. Al-

ternatively each rotor hub or transmission. may include a freewheel clutch, it being known prac" tice in this art to incorporate such clutch in the being either under the control of the pilot or automatic, so that in the event of a cessation of the drive the rotor pitches can be or are adjusted to a value within the autorotational range.

. Automatic means for performing this operation are disclosed in my copending application dated January 30, 1940, Serial Number 316,330 (Patent 2,325,632) which describes and claims'the' use of means responsive to the rotational speed of the rotors controlling, through an hydraulic relay mechanism, rotor pitch changing means.

Lateral control of the aircraft may be obtained by providing means for differential alteration of the pitch of each of the pair of rotors so that the lift of one rotor is increased while that of the other is decreased, these means being coupled to a pilots control column or analogous control so that sideways movement of the control column causes such differential pitch change.

Angular tilting of the lift lines of the two rotors may be used to give control of the aircraft in pitch and also in yaw, the former being obtained by simultaneous equal shifting of the lift linesof the rotors in a generally fore and aft direction by moving the pilots control column or analogous control in a backwards and forwards direction. The control of the aircraft in yaw normally obtained by a rudder bar or equivalent control, is provided by differential tilting of the lift lines of the two rotors so that while the lift line of one rotor is tilted forwardly the lift line of the other rotor is tilted backwardly.

The accompanying drawings illustrate by way of example a rotor transmission system, a rotor hub and control means for use therewith, all constructed in accordance with this invention.

In the drawings:

Fig. l is a diagrammatic rear elevation of the rotor transmission and control system;

Fig. 2 is a plan view corresponding to Fig. 1;

Fig. 3 is a sectional plan through a part of the rotor transmission system and the balance gear;

Fig. 3A is a continuation of Fig. 3 on the right hand side;

Fig. 4 is a section on the line IVIV of Fig. 3;

Fig. 5 is a sectional elevation of a rotor hub;

Fig. 5A is a continuation of Fig. 5 on the right hand side;

Fig. 6 is a fragmentary'elevation through the hub at right angles to Fig. 5;

Fig. 6A is a continuation of Fig. 6 on the right hand side;

Fig. 7 is a plan view of the rotor hub;

' Fig. 7A is a continuation of Fig. '7 on the right hand side; r

Fig. 8 is a fragmentary sectional plan view through the rotor hub at the general plane of attachment of the rotor blades;

Fig. 9 is a fragmentary elevational section showing the freewheel clutch incorporated in the rotor hub;

Fig. 10 is a rearelevational view, partly in section, showing the pitch control mechanism;

Fig. 11 is a sectional view on the line XII-XI of Fi 10;

Fig. 12 shows diagrammatically the control system;

Fig. 13 is an elevational view showing diagrammatically a modified arrangement in which the rotor hub axes are inclined upwardly towards each other to provide a dihedral action.

Referring to the drawings, Figs. 1 and 2. A helicopter has a pair of side-by-side rotors I00, 200 of similar construction which rotate in opposite directions. These are shown diagrammatically in Fig. 1 which shows them driven through shafts I M, 20I ,and bevel drives I02, 202 respectively. Below the rotor I00, as seen in Figures 1 and 12, is mounted a chain wheel I03 which is driven by a short length of chain coupled to control wires I04, I04a passing over pulleys I05, Ia from a sprocket I06 of the pitch change control hereinafter described. Below the chain wheel I03 is mounted a smaller chain wheel I01 which is coupled by control wires I08, I00a passing over pulleys I09, I09a to a pilot's control for effecting cyclic pitch change of the rotor, hereinafter described in detail with reference to Fig. 12. Similar arrangements are provided for the rotor 200, the parts corresponding to the parts I03 to I09a having reference numbers 203 to 209a.

The rotor drive shafts IOI, 20I are driven from a gearbox IIO on the centre line of the aircraft. An engine 599 drives the gearbox IIO through a fluid coupling 60!) and a spur type differential gear 650. These are illustrated diagrammatically in Fig. 2 and in detail in Figs. 3, 3A, and 4.

Referring to the latter figures: A bush 602 is secured on the engine shaft 60I by a screw nut 603 and splines (not shown) and to the inner edge of an annular flexible diaphragm 604 by bolts 605. The outer edge of the diaphragm 604 is bolted at 606 to the driving rotor member 601 of the fiuid coupling to which is secured a casing part 608 enclosing the other parts of the fluid coupling 600. The driven rotor member M0 is bolted at 6II to a flange 6I2 of the driven shaft 6I3 which extends from the fluid coupling 600 to the differential gear 650. An extension of the shaft 6I3 (towards the engine). carries a journal roller bearing 6 I4 which acts as a centering bearing between the driving and driven rotor members 601 and 6I0 respectively and also an oil seal 6I5. A shoulder 6I6 on the driven shaft 6I3 locates a journal ball-bearing 6I1 interposed between the shaft 6I3 and the casing part 608, the inner element of the bearing 6I1 being secured to the shaft 6I3 by a flanged ring 6I8 screwed onto said shaft while the outer element of the bearing is secured by a ring GIS! in a recess 620 in the casing part 608. carries a spring diaphragm 62I which presses a packing ring 622 into contact with a face 623 on the ring 6I9 thereby forming an oil seal.

If it is desired to disconnect the drive from the engine to the rotors this can be accomplished by means not shown which allow fluid to be taken out of the fluid coupling 600. Such disconnection of hydraulic couplings of this type is well known in the coupling art.

The flanged ring 6I8 It is thought unnecessary to describe in detail the construction of the rotor members 601 and Bio or the method of operation of the coupling since the provision of a suitable fluid coupling for transmitting the necessary power is within the competence of those skilled in the industry.

The driven shaft 6I3 of the fluid coupling 600 as above mentioned extends into the differential gear 650 and is journalled in the casing I by a bearing 652, the inner element of which is clamped on said shaft 6| 3 between the flanged ring 6I8 and a centering wedge ring 653. The outer element of the bearing 652 is held in a recess 654 in the casing 65I' by a locating plate 655 and annulus 656. The centering wedge ring 653 cooperates with a similar wedge ring 651 and a ring 658 mounted on a. screw thread 659 on the end of the shaft 6| 3 to secure to said shaft the carrier 660 of the differential gear.

The carrier 660 supports by means of roller journal bearings such as 66I held in recesses 662, hollow shafts 663 having shoulders 664 locating bushes 665 on which are carried hollow pinions 666. The teeth 661 formed on the exterior of the hollow pinions 666 only extend over about two thirds of the length of the pinions from one end as shown in Fig. 3. The carrier 660 carries two sets of such pinions, each set as illustrated consisting of three pinions disposed at 129 about the axis of the shaft 6 I3 (see Fig. 4). The pinion 666 which is illustrated in section in Fig. 3A is one of the set marked 666 in Fig. 4 while those of the other set are marked 610 and are similarly mounted on the carrier 660.

It will be understood that the teeth 661 of the pinions 666 extend from the right hand end (as shown in Fig. 3A) to a point about two thirds of the way along the pinion, the left hand end of which carries no teeth. The teeth of the pinions 610 extend a similar distance from the left hand end, while the right hand end is smooth. As shown in Fig. 4 the pairs of pinions 666 and 610 mesh together over their middle parts, while their toothed ends mesh with toothed wheels 61I and 612 respectively.

The wheel 61I (Fig. 3A) is formed on a stub shaft 613 journalled in the casing 614 by a ball bearing 615 the outer element of which is secured to the casing by a locating plate 616 and annulus 611. The inner element of the bearing 615 is clamped between a shoulder 618 on the stub shaft 613 and a bevel wheel 619 having an extended bush keyed at 680 to the stub shaft 613 and secured thereto by a screw threaded ring 68I engaged on a'screw thread 682 at the end of the stub shaft.

The bevel wheel 619 meshes with a bevel wheel 683 keyed at 684 and secured by a threaded ring 685 to the inner end of a shaft 686 through which the drive is transmitted to the port rotor. The shaft 686 is journalled at its inner end by a journal and thrust bearing 681, the inner element of which is clamped between a shoulder 608 on the shaft and the bevel wheel 683. The outer element of the bearing 681 is secured by a locating plate 689 and annulus 690 to a ring 69I carried by webs 692 within the casing 693 of the gearbox IIO. Near its outer end the shaft 686 is supported by a journal bearing 694 supported in an aperture 695 in the casing 693 and held in position by a clamping plate 696 and annulus 691. A flange 698 is secured to the end of the shaft 686 by a ring 699 which engages a screw thread on the end of the shaft. An extension of the flange serves to press the inner element of the tains it concentric with the stub shaft 613,'the:'-

I61 clamped to the liner I66 by a screw ring I68 which also secures a ball journal bearing I69 against a collar I10 on the liner. The outer member-of the ball bearing I69 is held in a recess "I in a cover plate I12 clamped to the housing I 50 by studs and nuts I13. The aperture in the cover plate I12 is a close fit over the liner 'I86 which passes through it and is provided with'a-dirt excluding packing I14.

outer element of thebearing being held in posi tion by a ring .123 engaging a screw thread 124 within the end of the stub shaft. 1

As seen in Figure 3A, the right hand end of the shaft 120 has a bevel wheel II25keyed at 126 to it and secured in position by a ring 121 engaging a screw thread 128 on the end of the shaft 120. A journal and thrust bearing 129.,supports this end of the shaft, being. clamped between the i bevel wheel 125 and the ring 121 while the outer element is held in position in an aperture 130 in the casing 614 by an annulus 13I'and cover plate 132. The bevel wheel 125 meshes'with abevel wheel 133 carried on a shaft 134 mountedin the same way as the shaft 686 and transmitting the drive to the port rotor drive shaft 20I. The gear ratio of the wheels 619 and 683 must of course be equal to the ratio of the wheels 125 and 133.

The differential gear 650 ensures that the torques of the two rotors shall be maintained substantially equal. The provision of free wheels in the drives to each of the rotors will however allow the torques absorbed by the rotors momentarily to be unequal when one or both of the rotors is overrunning the drive.

While no mention of an airscrew drive has'been made in the foregoing description it is to be understood that one or more airscrews for forward propulsion may be provided and be driven in a suitable manner from the engine 599 or from one or more other engines mounted within the fuselage or in engine nacelles carried by stub wings on either side of the fuselage. Since the dispos tion and arrangement of such propulsive airscrews is not an integral part of the rotor transmission and control means of the present invention it is thought unnecessary to describe it in greater detail. Alternatively a propulsive force may be obtained by simultaneous tilt ng of the lift lines of the pair of rotors so that the rotors in addition to providing a lift force component also provide a horizontal component. By

suitable inclination of the lift lines the direction of this horizontal component can be arranged to give motion in any direction.

The rotor pitch control unit is illustrated in Figs. and 11. It comprises a housing I50 having at one end a cylinder I5I in which a piston I52 with piston rings I53 is slidable. The cylinder head I54 secured to the housing I50 by studs and nuts I55 has a central passage I56 which communicates through a union I51 and a screwed pipe joint I58, I59 with a pipe I60 which leads to a pilot's or automatic rotor pitch control and thence to a source of oil pressure.

and oil retaining packing I94.

" Formed-ontheexterior of the sleeve I63 are coarse pitch left and right hand screw threads I15 and I16 which are similar to each other except in hand. These threads I15 and I16 are engaged respectively by projecting parts I11 and I18 on rack membersl19 and I which are of generally cylindrical shape and slide in guides I8I and I82 in the housing I 50 and have rack surfaces. I83 and I84 which engage pinions I85 and I86 on shafts I81 and I88 respectively. The shaft I81 is mounted in journal ball bearings I89 and I90 housed in recesses I9I and I92 in the housing I50 and is held in position by a ring I93 A flange I95 on the shaft I81 has a chain wheel 206 secured to it by bolts I96. The mounting of the shaft I88 is similar to that of the shaft I81 and it carries a chain wheel I06.

A rod 220 is attached to a projection 224 formed on the piston I52 by a ball joint comprising a ball 22I on the rod, a seating 222 and a screwed cap 223. The cap 223 is maintained against rotation by a split pin 225. The other end of the rod 220 is pivotally secured to the longer arm of a bell crank 226 pivoted at 221 to a bracket 228 mounted on the housing I50. The length of said longer arm of the bell crank 226 is adjustable by turning a central part 229, having left and right-hand threads 23!) and 23I, relatively to the ends 226 and, 232 of said arm. Screwed nuts 233 are provided for locking this central part 229 in the desired adjustment position. The shorter arm of the bell crank 226 is connected by a Bowden wire or analogous transmission 234 to a rotor pitch indicator in the pilots cockpit.

When oil pressure is applied from the pilots or automatic rotor pitch control through the pipe I60 to thecylinder I5I it causes the piston I52 to move to the right (Fig. 11) against the action of the spring I64. As it moves, the piston carries with it the sleeve I63 which slides over the liner I66. The sleeve I63 being secured to the rack members I19 and I80 by the projections I11 and I18 carries these rack members with it, causing rotation of the pinions I85, I86 in opposite directions, thereby rotating the chain wheel 206 counter-clockwise and the chain wheel I06 clockwise. These chain Wheels are coupled to-the rotor hubs to give equal increase of the pitch of each rotor. When the oil pressure is reduced, the piston I52 urged by the spring I64 moves back towards the left and causes equal reduction of pitch of the rotors.

Referring to Figures 1, l1 and 12, rotation of the sprocket I61 causes turning of the liner I56 and the sleeve I63 splined thereto relatively to the housing I50 and piston I52. This turning brings into play the opposite handed threads I15 and I16 and hence movement of the rack members I19 and I80 in opposite directions giving equal and opposite or different al pitch change of the two rotors. This differential pitch change of the rotors is arranged to provide control of the aircraft in roll. The sprocket I61 is coupled to a pilot's control column II5 so that when the column is moved sideways the rotor pitches are altered differentially, 4

The construction of a rotor hub is illustrated in Figs. 5 to 9. Each rotor blade 250 is secured at its root end to a root member 25! supported by journal ball bearings 252 and 253 and a ball thrust bearing 254 in a hollow'sleeve split into two parts 255 and 256 secured together by bolts 3 and nuts 251 (see Figures 7A and 8). Each of the parts 255, 256 forming the sleeve has a lug 258 with an aperture 259 forming a. housing for the roller bearing 260 of a flapping articulation (see Fig. 8). Each of the bearings 260 is held in position by a ring 26! with a locking screw 262, The pin members 263 of the flapping articulation are two opposite branches of a spider 264 having four branches in one plane mutually at right angles to each other. The branches 265, 210 form the inner members of a vertical drag articulation the axis of which intersects the flapping articulation at right angles. Plugs 266 are screwed into the ends of the pin members 263 which are hollow.

The drag articulation is best seen in Fig. 5A. The spider 264 has a pair of vertical pin members 265, 210 which form the inner parts of combined journal and thrust conical roller bearings 21! and 212. The outer part of the upper hear-- ing 21! is held in a recess 213 in a lug 214 extending from the rotating shell 215 of the hub, while the outer part of the lower bearing 212 is similarly held in a recess 216 in a member 211 surrounding the shell 215 and secured thereto by bolts 218 which pass through holes in lugs 219 and 280 on the shell 215 and member 211 respcctively.

A screwed plug 28! at the upper end of the upper pin member 265 rigidly secures thereto a plate 282 at each end of which links 283 are pivotally secured (see Fig. 1A). The other ends of these links 283 are pivotally secured to lugs 284 on plates 285 one for each 'blade arranged in pile form concentrically above the hub (see Fig. 5). Between adjacent plates 285 are arranged rings of friction material 286. The whole assembly forms a friction damper for movements about the drag articulations and is rotatable as a unit relatively to the shell 215 of the hub, together with a cover plate 340 of the hub.

As seen in Figures 5A and 8, a screwed plug 281 at the lower end of the lower pin member 210 holds in position a plate 288 which has a central apertur with a series of inwardly directed serrations 289. These serrations engage corresponding outwardly directed teeth 290 on the pin member 210 and allow the plate 288 and pin member 210 to be secured together in various rotational positions, The plug 281 is secured to the plate 288 by a set screw 29!. The plate 288 has.on its periphery stops 292 which cooperate with stops 293 on the housing 216 to limit movement of the blade about the drag articulation (see Fig. 8). By removing the plate 288 and re-engaging it in a difierent rotational position on the pin member 210 these limits can be altered.

The root member 25! of the blade has an inwardly directed extension-300 which terminates with a pair of arms which engage a circumferential groove 30! in a ball 302 the centre of which lies at the intersection of the flapping and drag axes. A similar groove 303 at right angles to the groove 30! is engaged by the forked arms 304 at one end of a shaft 305 which is supported in journal ball bearings 306 carried by a sleeve 301 which passes through the shell 215 and is screwed into a lug 308 thereon. Keyed to the inner end of the shaft 305, as seen in Figures 5 and 8, is a pitch change arm 309 which is secured in position by a bolt and nut 3!0 which clamp the split end of the arm 309 onto the shaft 305 and by a nut 3!! on the shaft 305.

At its free end the pitch change arm 309 has a pin 3l2 which extends generally radially outwards and carries a spherical seating member 3!3 held in position by a bolt 3!6 and cooperating with an internal spherical surface 3! 4 in an aperture at the upper end of a dependent pitch change link 3l5. At its lower end the pitch change link 3l5 has a similar surface 3" cooperating with a spherical seating member 3!8 held in position by a bolt 3!!! on a radial pin 320 carried by a swash plate 325.

The swash plate 325 is carried by bearings 326 and 321 on a spindle 328 which is tiltable in a vertical fore-and-aft plane about the axis of a pivot 329. The lower bearing 321 acts as a thrust and journal bearing while the upper, 326, separated from the former by a distance piece 330, is a journal bearing only and is secured by a nut 33! on the spindle 328. Secured by bolts 332 to the upper end 325a of the swash plate 325 is a lower element 333 of an universal joint 334 the other element 335 of which is secured to one part 336 of a link 336, 331 comprising two telescoping parts having splines 338 between them. The part 331 of the link is attached by an universal joint 339 to a flange of a cover plate 340 of the hub.

The cover plate 340 is bolted at 345 to an annular member 346 which supports the friction damper hereinbefore described and which is carried by journal bearings 341, 348 spaced by a distance piece 349 and secured by a nut 350 on an upwardly extending flange 35! of a bridge plate 352 secured to the upper end of the shell 215 of the hub by bolts 353.

It will be seen that the above-described connection between the swash plate 325 and the cover plate 340 ensures that they turn simul taneously while permitting vertical movement between them. Thus when the annular member 346 carrying the friction damper for lead-lag movements of the blades moves relatively to the shell 215 it turns the swash plate and prevents any pitch change due to such movement.

The spindle 328 has formed integrally with it a bell crank having two parallel arms 360 spaced apart and also a transverse bush 36! through which passes the pivot 329 carrying at each end a journal ball bearing 362 secured in position by a nut 363. The outer parts of the bearings 362 are supported by bushes 364 in flanges 365 extending upwardly from a crosshead 366 which is vertically slidable relatively to a fixed part 361 of the hub and is maintained against rotation by a keyway 359. The crosshead 366 has an internal flange 368 to which a flange 369 of a member 310 having coarse pitch internal and external screw threads, is secured by bolts 31!.

The external thread on the member 310 is engaged by an internally screw threaded ring 312 supported by thrust bearings 313, which prevent vertical movement, in the fixed part 361 of the hub. The thrust bearings 313 have between them an oil retaining packing ring 314 and are held in position by a clamping ring 315. Bolted at 316 to the lower end of the ring 312 is a chain wheel !03 by which, as previously mentioned, the pitch of the rotor is controllable.

When the chain wheel I03 is turned it turns the ring 312, the screw thread on which causes the member 310 and crosshead 366 to move vertically carrying with it the pivot 329, spindle 320 and swash plate 325. Since the lower ends of the pitch change links 3I5 are secured to the swash plate 325 they transmit the vertical moveis formed by an apertured lug 383 of a connecting link 384. A second needle roller bearing 305 is similarly mounted in an apertured lug 386 at the other end of the connecting link 384. The inner element of the bearing 385 is carried on a bolt 381 secured by a nut 388 and extending between flanges 389 at the upper end of a central member 390. The latter is secured to a sleeve 39I by combined journal and thrust bearings 392 which allow relative rotation but no axial movement between the central member 390 and sleeve 3,9I. The bearings 392 are secured to the central member by a ring 393 and distance piece 394 and are similarly secured by a ring 395 and distance piece 396 to the sleeve 39!.

The sleeve 39I has a flanged part 391 with an external screw thread cooperating with the internal screw thread on the member 310. On the exterior of the generally cylindrical part of the sleeve 39I are formed projections 398 which engage keyways 399 in the elongated bush 400 of the chain wheel I01. These keyways 399 permit the sleeve 39I to move vertically relatively to the hub but transmit to it rotational movementsof the chain wheel I01. The bush 400 is supported by combined journal and thrust bearings 40I which are secured on the bush by a ring 402 and distance piece 403 and on the bush 404 of the chain wheel I03 by a ring 405and distance piece 406.

When the chain wheel I01 is rotated it turns the sleeve 39I which moves vertically under the action of the screw threads on its flanged part 391 carrying with it the central member 390 and the lower end of the arms 360 of the bell crank which tilts the spindle 328 integral therewith. This tilts the swash plate 325 so that as it rotates with the rotor the lower ends of the pitch change links 3I5 move vertically up and down causing cyclic pitch change.

The rotors are driven from the common gearbox IIO by shafts IOI and 20I. As seen in Figure 5A, the end of the shaft IOI nearest the rotor I00 has a flange not shown which is bolted to a flange 500 secured on a shaft 50I by keys 502 and a ring 503 screwed onto the shaft. The shaft 50I is carried in ball bearings 504 and a roller bearing 505 within a sleeve 506 slidable within a cylindrical projection from the main non-rotating part 361 of the hub. This sleeve provides means for locating the shaft in correct axial position so that a pinion 501 on the shaft 50I meshes properly with the crown wheel ring I02 of the rotor. This axial adjustment is provided by shims 508 interposed between a flange 509 on the sleeve 506 and a ring 5I0 clamped by studs and nuts 5 to the hub part 361. The ring 5I0 clamps the bearings 504, 505 and a distance piece 5I2 within the sleeve 506 and also provides a housing for an oil-retaining packing 5I3. On the shaft 50I the bearings and a distance piece 5I4 gag secured by the clamping action of the ring The crown wheel ring I02 is bolted at 5I5 to an annulus 5I6 supported within the non-rotating part 361 of the hub by combined journal and thrust bearing 5I1, 5I8 supported by parts 5I9 and 520 respectively which latter are secured by studs and'nuts' MI and 522'to the hub part 361. An oil-retaining packing 523 is held by a ring 524 carried by the part 520.

Reference should now be made to Figure 9, in

conjunction with Figure 5.

An axially slidable member 525 is attached by splines 526 to the inner surface of the annulus 5I6 and is urged upwardly by springs 521 surrounding rods 528 carried bya lower spacer 529 and by holes 530 in the member 525. The upper end of the member 525 has a series of dog clutch surfaces 53I spaced 120 (the same angle as that between the rotor blades) and backed off by inclined surfaces 532. These clutch surfaces 53I are adapted to engage corresponding surfaces 533 projecting downwardly from an upper clutch member 534, which also has inclined surfaces 535 corresponding to the inclined surfaces 532. The upper clutch member 534 is secured by the bolts 218 to the shell 215 and is supported near its upper end by a journal and thrust bearing 536 supported by the part 5I9 on the stationary part of the hub. While the rotor is being driven the surfaces 53I and 533 engage but when the rotor is over-running the drive, the member 525 is pressed downwardly against the action of the springs 521 by the inclined surfaces 532 and 535.

The lower end of the shell 215 is supported by a thrust andjournal bearing 550 between said shell and the annulus 5I6. Secured to the lower end of the shell 215 is a rotor brake drum 55I held in position by a ring 552. The brake has two shoes 553 with surfaces of friction material. One end of each of the shoes 553 is pivotally connected at 556 to the stationary hub part 361, the pivot pin 556 being secured by a screw nut 551. The other ends of the brake shoes ar held by a spring in contact with control plungers which move in a common cylinder 559 into the central part of which oil under pressure is introduced through a passage 560 when it is'desired to stop the rotor.

Fig. 12 shows diagrammatically the rotor control system adapted for dual control, the pilots being seated in tandem. Two control columns II5, 511 are mounted on bail joints 100, a so as to be movable in any direction. The column H5 is coupled to the column II5iz by a shaft 10I having an universal joint (not shown) at each end so that lateral movements of the columns are rotor pitch is reduced while that of the port rotor is increased.

The control columns H5 and II5a are coupled together for equal fore and aft movement by a link 1I0 pivotally secured at its ends to the control columns. As illustrated the link H0 is arranged above the ball mountings 100 but if desided it could be arranged below. Reference has 

